SPACECRAFT POWER SUPPLY SYSTEM CONTROL METHOD Russian patent published in 2018 - IPC H02J7/34 

FIELD: electrical engineering.

SUBSTANCE: power supply system control method of a spacecraft (SC) containing a photovoltaic battery (PB) and n storage batteries (SB), voltage regulator and by n charging and discharging devices, consists of the control over the voltage regulator, charging and discharging devices, depending on the PB illumination, of all SB charge state, input and output voltage (PSS); introduction of the corresponding discharging device operation prohibition, when reaching the given SB established minimum of charge level, and this prohibition lifting when the given SB level of charge is increasing; generating a control signal to the SC onboard control system for switching off a part of the onboard equipment (OE) during the several m (m≤n) SB emergency discharge to the minimum charge level, prohibiting all of the discharging devices operation, if the PSS output voltage drops to the predetermined threshold value; performing the control signal memorization resetting by all of the discharging devices prohibit after all of the SB charging to the given level of charge. SC power supply system PB energy use degree (ratio) is determined by the calculation and experimental method, for which: as the maximum nominal power (N_nom.) choosing the PB power rated value, corresponding to the power at the current-voltage characteristic operating point with the PB maximum illumination (h₀); change in the PB current nominal power (N_rated) from time (t) analytical dependence taking to be proportional to the current illumination h=h₀⋅cosα, where h₀=1, α is the angle between the PB plane vector and direction to the Sun; making the selected analytical dependence diagram in the scale, and determining corresponding to the PB maximum generated energy figure area, bounded by the vertical straight lines t=0 and t=T_light., the horizontal line N=0 and the curve, determined by the N=N_nom⋅h(t) dependence, where T_light is the of the of the SC orbit light portion duration, h(t) is the law (cyclogram) of the change in the PB illumination over time in the process of the particular spacecraft movement on the light portion of its orbit, using for the figure area calculation, for example, the Simpson method; performing the similar sequence of operations for the specific spacecraft PB, at that, to determine the PB power actual current value, using the N=I_PB(t)⋅U_PB(t) ratio, where I_PB(t), U_PB(t) are telemetered current values of PB current and voltage, respectively. PB actual energy determination is carried out for m≥2 turns, then calculating its average value per one turn; comparing the maximum energy magnitude and the PB actual energy average value among themselves judging the PB energy use degree of the BF during the PSS normal operation.

EFFECT: reducing the emergency likelihood due to the power supply system (PPS) energy balance violation.

1 cl, 5 dwg